127 

Federal Aviation Administration, DOT 

§ 121.313 

requirements pertaining to seat cush-
ions in § 25.853(c) effective on November 
26, 1984, on each airplane as follows: 

(1) Each transport category airplane 

type certificated after January 1, 1958; 
and 

(2) On or after December 20, 2010, 

each nontransport category airplane 
type certificated after December 31, 
1964. 

(c) 

All interior materials; airplanes type 

certificated in accordance with SFAR No. 
41 of 14 CFR part 21. 

No person may op-

erate an airplane that conforms to an 
amended or supplemental type certifi-
cate issued in accordance with SFAR 
No. 41 of 14 CFR part 21 for a maximum 
certificated takeoff weight in excess of 
12,500 pounds unless the airplane meets 
the compartment interior require-
ments set forth in § 25.853(a) in effect 
March 6, 1995 (formerly § 25.853(a), (b), 
(b–1), (b–2), and (b–3) of this chapter in 
effect on September 26, 1978)(see app. L 
of this part). 

(d) 

All interior materials; other air-

planes. 

For each material or seat cush-

ion to which a requirement in para-
graphs (a), (b), or (c) of this section 
does not apply, the material and seat 
cushion in each compartment used by 
the crewmembers and passengers must 
meet the applicable requirement under 
which the airplane was type certifi-
cated. 

(e) Thermal/acoustic insulation ma-

terials. For transport category air-
planes type certificated after January 
1, 1958: 

(1) For airplanes manufactured before 

September 2, 2005, when thermal/acous-
tic insulation is installed in the fuse-
lage as replacements after September 
2, 2005, the insulation must meet the 
flame propagation requirements of 
§ 25.856 of this chapter, effective Sep-
tember 2, 2003, if it is: 

(i) Of a blanket construction or 
(ii) Installed around air ducting. 
(2) For airplanes manufactured after 

September 2, 2005, thermal/acoustic in-
sulation materials installed in the fu-
selage must meet the flame propaga-
tion requirements of § 25.856 of this 
chapter, effective September 2, 2003. 

(3) For airplanes with a passenger ca-

pacity of 20 or greater, manufactured 
after September 2, 2009, thermal/acous-
tic insulation materials installed in 

the lower half of the fuselage must 
meet the flame penetration resistance 
requirements of § 25.856 of this chapter, 
effective September 2, 2003. 

[Doc. No. 28154, 60 FR 65930, Dec. 20, 1995, as 
amended by Amdt. 121–301, 68 FR 45083, July 
31, 2003; Amdt. 121–320, 70 FR 77752, Dec. 30, 
2005; Amdt. 121–330, 72 FR 1442, Jan. 12, 2007; 
Docket FAA–2018–0119, Amdt. 121–380, 83 FR 
9173, Mar. 5, 2018] 

§ 121.313 Miscellaneous equipment. 

No person may conduct any oper-

ation unless the following equipment is 
installed in the airplane: 

(a) If protective fuses are installed on 

an airplane, the number of spare fuses 
approved for that airplane and appro-
priately described in the certificate 
holder’s manual. 

(b) A windshield wiper or equivalent 

for each pilot station. 

(c) A power supply and distribution 

system that meets the requirements of 
§§ 25.1309, 25.1331, 25.1351(a) and (b)(1) 
through (4), 25.1353, 25.1355, and 
25.1431(b) or that is able to produce and 
distribute the load for the required in-
struments and equipment, with use of 
an external power supply if any one 
power source or component of the 
power distribution system fails. The 
use of common elements in the system 
may be approved if the Administrator 
finds that they are designed to be rea-
sonably protected against malfunc-
tioning. Engine-driven sources of en-
ergy, when used, must be on separate 
engines. 

(d) A means for indicating the ade-

quacy of the power being supplied to 
required flight instruments. 

(e) Two independent static pressure 

systems, vented to the outside atmos-
pheric pressure so that they will be 
least affected by air flow variation or 
moisture or other foreign matter, and 
installed so as to be airtight except for 
the vent. When a means is provided for 
transferring an instrument from its 
primary operating system to an alter-
nate system, the means must include a 
positive positioning control and must 
be marked to indicate clearly which 
system is being used. 

(f) A door between the passenger and 

pilot compartments (

i.e.

, flightdeck 

door), with a locking means to prevent 
passengers from opening it without the 

128 

14 CFR Ch. I (1–1–24 Edition) 

§ 121.314 

pilot’s permission, except that non-
transport category airplanes certifi-
cated after December 31, 1964, are not 
required to comply with this para-
graph. For airplanes equipped with a 
crew rest area having separate entries 
from the flightdeck and the passenger 
compartment, a door with such a lock-
ing means must be provided between 
the crew rest area and the passenger 
compartment. 

(g) A key for each door that sepa-

rates a passenger compartment from 
another compartment that has emer-
gency exit provisions. Except for 
flightdeck doors, a key must be readily 
available for each crewmember. Except 
as provided below, no person other 
than a person who is assigned to per-
form duty on the flightdeck may have 
a key to the flightdeck door. Before 
April 22, 2003, any crewmember may 
have a key to the flightdeck door but 
only if the flightdeck door has an in-
ternal flightdeck locking device in-
stalled, operative, and in use. Such 
‘‘internal flightdeck locking device’’ 
has to be designed so that it can only 
be unlocked from inside the flightdeck. 

(h) A placard on each door that is the 

means of access to a required passenger 
emergency exit, to indicate that it 
must be open during takeoff and land-
ing. 

(i) A means for the crew, in an emer-

gency to unlock each door that leads to 
a compartment that is normally acces-
sible to passengers and that can be 
locked by passengers. 

(j) After April 9, 2003, for airplanes 

required by paragraph (f) of this sec-
tion to have a door between the pas-
senger and pilot or crew rest compart-
ments, and for transport category, all- 
cargo airplanes that have a door in-
stalled between the pilot compartment 
and any other occupied compartment 
on January 15, 2002; 

(1) After April 9, 2003, for airplanes 

required by paragraph (f) of this sec-
tion to have a door between the pas-
senger and pilot or crew rest compart-
ments, 

(i) Each such door must meet the re-

quirements of § 25.795(a)(1) and (2) in ef-
fect on January 15, 2002; and 

(ii) Each operator must establish 

methods to enable a flight attendant to 
enter the pilot compartment in the 

event that a flightcrew member be-
comes incapacitated. Any associated 
signal or confirmation system must be 
operable by each flightcrew member 
from that flightcrew member’s duty 
station. 

(2) After October 1, 2003, for transport 

category, all-cargo airplanes that had a 
door installed between the pilot com-
partment and any other occupied com-
partment on or after January 15, 2002, 
each such door must meet the require-
ments of § 25.795(a)(1) and (2) in effect 
on January 15, 2002; or the operator 
must implement a security program 
approved by the Transportation Secu-
rity Administration (TSA) for the oper-
ation of all airplanes in that operator’s 
fleet. 

(k) Except for all-cargo operations as 

defined in § 110.2 of this chapter, for all 
passenger-carrying airplanes that re-
quire a lockable flightdeck door in ac-
cordance with paragraph (f) of this sec-
tion, a means to monitor from the 
flightdeck side of the door the area 
outside the flightdeck door to identify 
persons requesting entry and to detect 
suspicious behavior and potential 
threats. 

(l) For airplanes required by para-

graph (f) of this section to have a door 
between the passenger and pilot or 
crew rest compartments, and for pas-
senger-carrying transport category air-
planes that have a door installed be-
tween the pilot compartment and any 
other occupied compartment, that were 
manufactured after August 25, 2025, an 
installed physical secondary barrier 
(IPSB) that meets the requirements of 
§ 25.795(a)(4) of this chapter in effect on 
August 25, 2023. 

[Doc. No. 6258, 29 FR 19205, Dec. 31, 1964, as 
amended by Amdt. 121–5, 30 FR 6113, Apr. 30, 
1965; Amdt. 121–251, 60 FR 65931, Dec. 20, 1995; 
Amdt. 121–288, 67 FR 2127, Jan. 15, 2002; Amdt. 
121–299, 68 FR 42881, July 18, 2003; Amdt. 121– 
334, 72 FR 45635, Aug. 15, 2007; Amdt. 121–353, 
76 FR 7488, Feb. 10, 2011; Amdt. No. 121–389, 88 
FR 41308, June 26, 2023] 

§ 121.314 Cargo and baggage compart-

ments. 

For each transport category airplane 

type certificated after January 1, 1958: 

(a) Each Class C or Class D compart-

ment, as defined in § 25.857 of this Chap-
ter in effect on June 16, 1986 (see Ap-
pendix L to this part), that is greater